Effect of propellant composition to the temperature sensitivity of composite propellant

The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had...

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Main Authors:	Amir, Aziz, R., Mamat, Amin, Makeen, Wan Khairuddin, Wan Ali
Format:	Conference or Workshop Item
Language:	English
Published:	IOP Publishing 2012
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf

id	ump-25159
recordtype	eprints
spelling	ump-251592019-11-11T06:47:15Z http://umpir.ump.edu.my/id/eprint/25159/ Effect of propellant composition to the temperature sensitivity of composite propellant Amir, Aziz R., Mamat Amin, Makeen Wan Khairuddin, Wan Ali TJ Mechanical engineering and machinery The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of ammonium perchlorate (AP) as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer- fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1 atm to 31 atm. The results obtained shows that the temperature sensitivity, a, increases with increasing O/F. Propellant p80 which has O/F ratio of 80/20 gives the highest value of temperature sensitivity which is 1.687. The results shows that the propellant composition has significant effect on the temperature sensitivity of composite propellant. IOP Publishing 2012 Conference or Workshop Item PeerReviewed pdf en http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf Amir, Aziz and R., Mamat and Amin, Makeen and Wan Khairuddin, Wan Ali (2012) Effect of propellant composition to the temperature sensitivity of composite propellant. In: 1st International Conference on Mechanical Engineering Research, ICMER 2011, 5-7 Disember 2011 , Kuantan, Pahang Darul Makmur. pp. 1-7., 36 (012023). ISSN 1757-899X https://doi.org/10.1088/1757-899X/36/1/012023
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Malaysia Pahang
building	UMP Institutional Repository
collection	Online Access
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Amir, Aziz R., Mamat Amin, Makeen Wan Khairuddin, Wan Ali Effect of propellant composition to the temperature sensitivity of composite propellant
description	The propellant composition is one of several parameter that influencing the temperature sensitivity of composite propellant. In this paper, experimental investigation of temperature sensitivity in burning rate of composite propellant was conducted. Four sets of different propellant compositions had been prepared with the combination of ammonium perchlorate (AP) as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as fuel and binder. For each mixture, HTPB binder was fixed at 15% and cured with isophorone diisocyanate (IPDI). By varying AP and Al, the effect of oxidizer- fuel mixture ratio (O/F) on the whole propellant can be determined. The propellant strands were manufactured using compression molded method and burnt in a strand burner using wire technique over a range of pressure from 1 atm to 31 atm. The results obtained shows that the temperature sensitivity, a, increases with increasing O/F. Propellant p80 which has O/F ratio of 80/20 gives the highest value of temperature sensitivity which is 1.687. The results shows that the propellant composition has significant effect on the temperature sensitivity of composite propellant.
format	Conference or Workshop Item
author	Amir, Aziz R., Mamat Amin, Makeen Wan Khairuddin, Wan Ali
author_facet	Amir, Aziz R., Mamat Amin, Makeen Wan Khairuddin, Wan Ali
author_sort	Amir, Aziz
title	Effect of propellant composition to the temperature sensitivity of composite propellant
title_short	Effect of propellant composition to the temperature sensitivity of composite propellant
title_full	Effect of propellant composition to the temperature sensitivity of composite propellant
title_fullStr	Effect of propellant composition to the temperature sensitivity of composite propellant
title_full_unstemmed	Effect of propellant composition to the temperature sensitivity of composite propellant
title_sort	effect of propellant composition to the temperature sensitivity of composite propellant
publisher	IOP Publishing
publishDate	2012
url	http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/ http://umpir.ump.edu.my/id/eprint/25159/1/Effect%20of%20propellant%20composition%20to%20the%20temperature%20sensitivity%20of%20composite%20propellant.pdf
first_indexed	2023-09-18T22:38:29Z
last_indexed	2023-09-18T22:38:29Z
_version_	1777416755777372160

Effect of propellant composition to the temperature sensitivity of composite propellant

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